DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
ADA243916
Title:
Finite Element Analysis of a Riveted Repair on a Curved Composite Panel
Descriptive Note:
Master's thesis
Corporate Author:
AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
Report Date:
1991-12-01
Pagination or Media Count:
119.0
Abstract:
To analyze the current Aircraft Battle Damage Repair ABDR techniques, a finite element model FEM of a curved composite panel with a center cutout section was developed and verified against previously obtained modal test results. The FEM was modified using different methods to exhibit the effects of riveting on an aluminum patch to repair the section. The different methods were contrasted against each other and previously obtained modal test results. The panel, a 0-454590 sub s layup of AS43501 graphite epoxy measuring 12 inches in height and 12.19 inches across its arc length with a 2 by 4 inch cutout at a 0, 45, -45, or 90 degree orientation was modeled using MSCNASTRAN QUAD4 elements. The first repair modeling method used a mixture of the aluminum and composite panel properties to represent the overlap region of the patch. The second method used ELAS2 and CONM2 elements to model the rivets, and modelled the panel and the patch separately. GAP elements prevented the patch from deforming through the panel. For the mixed properties, the mode shapes agreed with experimental data at lower frequencies but were distorted at the higher ones and were regularly 5-25 high. Modeling the rivets individually produced matching mode shapes and frequencies regularly within 5 of experimental values.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
